CN109204836A - A kind of unmanned plane air crash protective device - Google Patents
A kind of unmanned plane air crash protective device Download PDFInfo
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- CN109204836A CN109204836A CN201810920264.7A CN201810920264A CN109204836A CN 109204836 A CN109204836 A CN 109204836A CN 201810920264 A CN201810920264 A CN 201810920264A CN 109204836 A CN109204836 A CN 109204836A
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- unmanned plane
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- 230000001681 protective effect Effects 0.000 title claims abstract description 40
- 230000009467 reduction Effects 0.000 claims abstract description 34
- 230000007246 mechanism Effects 0.000 claims description 106
- 230000007704 transition Effects 0.000 claims description 47
- 238000013016 damping Methods 0.000 claims description 19
- 238000003466 welding Methods 0.000 claims description 19
- 229910000831 Steel Inorganic materials 0.000 claims description 17
- 230000005540 biological transmission Effects 0.000 claims description 17
- 239000010959 steel Substances 0.000 claims description 17
- 230000006835 compression Effects 0.000 claims description 14
- 238000007906 compression Methods 0.000 claims description 14
- 241000883990 Flabellum Species 0.000 claims description 9
- 238000009434 installation Methods 0.000 claims description 9
- 238000005096 rolling process Methods 0.000 claims description 3
- 238000003780 insertion Methods 0.000 claims description 2
- 230000037431 insertion Effects 0.000 claims description 2
- 206010057071 Rectal tenesmus Diseases 0.000 abstract description 7
- 208000012271 tenesmus Diseases 0.000 abstract description 7
- 230000035939 shock Effects 0.000 abstract description 5
- 230000005484 gravity Effects 0.000 abstract description 4
- 230000000694 effects Effects 0.000 abstract description 3
- 238000010586 diagram Methods 0.000 description 4
- 230000006870 function Effects 0.000 description 3
- 230000009471 action Effects 0.000 description 2
- 230000008901 benefit Effects 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000008450 motivation Effects 0.000 description 2
- 238000009527 percussion Methods 0.000 description 2
- 208000035473 Communicable disease Diseases 0.000 description 1
- 241001465754 Metazoa Species 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 208000015181 infectious disease Diseases 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000013507 mapping Methods 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 description 1
- 230000008569 process Effects 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D17/00—Parachutes
- B64D17/80—Parachutes in association with aircraft, e.g. for braking thereof
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/58—Arrangements or adaptations of shock-absorbers or springs
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D17/00—Parachutes
- B64D17/40—Packs
- B64D17/52—Opening, e.g. manual
- B64D17/54—Opening, e.g. manual automatic
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U70/00—Launching, take-off or landing arrangements
- B64U70/80—Vertical take-off or landing, e.g. using rockets
- B64U70/83—Vertical take-off or landing, e.g. using rockets using parachutes, balloons or the like
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Vibration Prevention Devices (AREA)
Abstract
The invention discloses a kind of unmanned plane air crash protective devices; its structure includes that mechanical arm, auxiliary rotatable paddle wheel, power paddle wheel, observation camera, support rod, reduction of speed buffer protection device is fixedly mounted; one end that mechanical arm is fixedly mounted is equipped with power paddle wheel and is connected by way of rotation; the other end that mechanical arm is fixedly mounted is connected by way of bonding with the outer surface of reduction of speed buffer protection device, and the front of rotatable paddle wheel is assisted to be equipped with power paddle wheel.The present invention is when unmanned plane failure is fallen; it being capable of pop-up parachute pack promptly and accurately; increase air drag; slow down the speed of unmanned plane tenesmus; gravity inertial power and the impact force being subject to behind bottom surface so that unmanned plane falls substantially reduce; then the floor stand of bottom can further play shock absorbing effect after unmanned plane and bottom surface contact, and prevent unmanned plane components from loosening, to carry out unmanned plane protection.
Description
Technical field
The present invention relates to unmanned plane fields, more precisely, being a kind of unmanned plane air crash protective device.
Background technique
UAV referred to as " unmanned plane ", is manipulated using radio robot and the presetting apparatus provided for oneself
Not manned aircraft, or fully or intermittently automatically operated by car-mounted computer at present take photo by plane, it is agricultural, plant protection, micro-
Type self-timer, express transportation, disaster relief, observation wild animal, monitoring infectious disease, mapping, news report, electric inspection process, the disaster relief,
The application in movies-making, manufacture romance etc. field, still, current this unmanned plane has the following disadvantages:
1, not perfect for the safeguard measure of UAV Components when unmanned plane failure air crash, power can not be unloaded in time
Protection, causes unmanned plane when falling, since suffered inertia force is big, directly causes unmanned plane to damage with collision on the ground.
2 and unmanned plane landing when ground, generate biggish impact force, easily lead to unmanned plane inner components generation
It loosens and shifts, influence the function of unmanned plane.
Summary of the invention
In view of the deficienciess of the prior art, it is an object of the present invention to provide a kind of unmanned plane air crash protective device, to solve
The prior art when unmanned plane failure air crash, it is not perfect for the safeguard measure of UAV Components, power can not be unloaded in time
Protection, causes unmanned plane when falling, since suffered inertia force is big, directly causes unmanned plane to damage with collision on the ground, and nothing
It is man-machine to land when ground, biggish impact force is generated, unmanned plane inner components is easily led to and occurs to loosen and shift, influence
The defect of the function of unmanned plane.
To achieve the goals above, the present invention is to realize by the following technical solutions:
A kind of unmanned plane air crash protective device, structure include that mechanical arm, auxiliary rotatable paddle wheel, power blade is fixedly mounted
Wheel, observation camera, support rod, reduction of speed buffer protection device, described one end that mechanical arm is fixedly mounted are equipped with power blade
It takes turns and is connected by way of rotation, the appearance of the other end that mechanical arm is fixedly mounted and reduction of speed buffer protection device
Face is connected by way of bonding, and the front of the auxiliary rotatable paddle wheel is equipped with power paddle wheel, the observation camera
It is installed on the bottom end that mechanical arm is fixedly mounted and is connected by welding, the support rod is set to reduction of speed buffer protection
The bottom end of device and it is connected by way of bonding, the surface of the observation camera is equipped with power paddle wheel, described
Reduction of speed buffer protection device includes outside protective covers shell, Wind assistor mechanism, mechanical transition transmission mechanism, magnetic fields gear
Structure, reduction gearing mechanism, overturning transition mechanism, compression pushing mechanism, damping linkage mechanism, the inside of the outside protective covers shell are embedding
There is Wind assistor mechanism and be connected by way of rotation, mechanical transition is installed on the right side of the Wind assistor mechanism and is passed
Motivation structure and it is connected by way of sliding, the top of the machinery transition transmission mechanism is equipped with magnetic fields linkage mechanism
And by mechanical connection, the reduction gearing mechanism is installed on the surface of magnetic fields linkage mechanism and passes through electric signal
Connection, the magnetic fields linkage mechanism are installed on the lower section of overturning transition mechanism and are connected by way of rotation, institute
The two sides for stating reduction gearing mechanism are equipped with overturning transition mechanism and are connected by way of bonding, the compression promotion machine
Structure is connected with damping linkage mechanism by electric signal, and mechanical transition transmission mechanism is equipped on the right side of the damping linkage mechanism
And pass through mechanical transition connection.
As the present invention, further scheme, the Wind assistor mechanism are equipped with turned flabellum, connection shaft, linkage
Scroll bar, cooperation turbine, connection belt, linkage rotary column, the one end of the top of the turned flabellum embedded with connection shaft and
It is connected by way of rotation, the other end of the connection shaft is connected by welding with linkage scroll bar, described
The back side of linkage scroll bar is equipped with cooperation turbine and is rotatablely connected by way of engagement, and the cooperation turbine passes through connection belt
With linkage rotary column rotation connection, the linkage rotary column is connected by way of sliding with mechanical transition transmission mechanism.
As further scheme of the invention, the machinery transition transmission mechanism is equipped with sliding block, sliding chute rod, connection push away repeatedly
Bar, linkage gear, movable rack, the sliding block repeatedly are installed on the outer surface of linkage rotary column and are connected by way of sliding
It connecing, the outside of the sliding chute rod is nested with sliding block repeatedly and is connected by way of sliding, and the one of the connection push rod
End is fixedly installed in repeatedly the front surface of sliding block and is connected by way of rotation, and the other end of the connection push rod is set to
It linkage gear and is rotatablely connected, the outside of the linkage gear is meshed with movable rack, and the movable rack and magnetic field are made
Pass through mechanical transition connection with linkage mechanism, the movable rack and damping linkage mechanism are mechanically connected.
As the present invention, further scheme, the magnetic fields linkage mechanism are equipped with battery, field coil, electrode
Circle, resets disc spring, determines cathode contact dynamic cathode contact, and field coil is equipped with above the battery and is passed through
Electric signal is connected, and the inside of the field coil is embedded with electrode collar, and the back side of the electrode collar, which is equipped with, resets disc spring simultaneously
And be connected by way of bonding, the outer surface of the electrode collar is connected by welding with dynamic cathode contact, institute
The top for stating cathode contact, which is equipped with, determines cathode contact, described to determine cathode contact and be connected with reduction gearing mechanism by electric signal
It connects, the electrode collar is connect with overturning transition mechanism by mechanical transition.
As the present invention, further scheme, the reduction gearing mechanism are equipped with fixed electromagnet, moving armature, limit cunning
Rail, mandril, parachute pack, the fixed electromagnet are connected with cathode contact is determined, and the top of the fixed electromagnet is equipped with
Moving armature and it is connected by magnetic force, the top of the moving armature is connected by welding with mandril, described
Moving armature is connected by way of sliding with limit sliding rail, and outer surface and the overturning transition mechanism of the limit sliding rail pass through
The mode of bonding is connected, and parachute pack is equipped with above the mandril and is connected by way of fitting.
As the present invention, further scheme, the overturning transition mechanism are equipped with connection steel wire, guiding fixed pulley, transmission belt
Wheel, protective cover, reset spring, the connection steel wire are connected by way of rolling with the outside for being oriented to fixed pulley, the company
The other end for connecing steel wire is set to drive pulley and is connected by way of rotation, the bottom end of the drive pulley and protective cover
Rotation connection, one end of the reset spring are connected by way of bonding with the inside of protective cover, the reset spring
The other end is connected by welding with sliding rail, and the head end of the connection steel wire is connected with electrode collar.
As the present invention further scheme, the compression pushing mechanism equipped with link block, mounting seat, float electrode,
Guide sleeve, stationary electrode, the top of the link block are equipped with mounting seat and are connected by way of bonding, the installation
The inside of pedestal is equipped with float electrode, and the inside of the guide sleeve is connected by way of nested with stationary electrode, described
Mounting seat is connected by way of sliding with guide sleeve, and the stationary electrode is connected with damping linkage mechanism by electric signal
It connects.
As the present invention further scheme, the damping linkage mechanism be equipped with Electromagnetic Control core, compressed air bag, into
Gas check valve, aerated rubber loop pad, the Electromagnetic Control core are connected with stationary electrode by electric signal, the Electromagnetic Control
Movable rack is installed on the right side of core and is connected by mechanical transition, it is empty that the bottom end of the Electromagnetic Control core is equipped with compression
Gas bag and it is connected by welding, the compressed air bag is connected with breather check valve, the breather check valve
Insertion is installed on the inside of aerated rubber loop pad.
Invention beneficial effect
A kind of unmanned plane air crash protective device of the invention, when unmanned plane failure air crash, due to being affected by gravity,
So that unmanned plane accelerates tenesmus, so that stronger wind-force can be generated around unmanned plane, and wind-force overcomes connection shaft and protection outer
Biggish stiction drives the rotation of turned flabellum between housing, so that co-axial connection shaft follows and turns together
Dynamic, drive is rotated with the linkage scroll bar that shaft is mutually welded is connect, so that the cooperation turbine rotation being meshed with linkage scroll bar, then
By connecting belt transmitting rotary power, so that rotation is followed with the linkage rotary column that belt is connected is connect, so that linkage
Rotary column drives repeatedly sliding block to slide up and down along the outer surface of sliding chute rod, so that pushing away with the connection that sliding block front surface is connected repeatedly
Bar movement pushes linkage gear rotation, drives the movable rack being meshed with linkage gear to move up, makes battery and electromagnetism
Control core is connected, and Electromagnetic Control core control field coil obtains electric generation field of magnetic forece, and electrode collar is pushed to drive dynamic anode touching
Point rotation, compression reset disc spring, at the same make dynamic cathode contact with determine cathode contact and be in contact, the production of fixed electromagnet conduction
Raw repulsion, the direction upward sliding for pushing moving armature to drive mandril along limit sliding rail eject parachute pack, while electrode
Circle drives one end rotary wire-reeling for the connection steel wire being fixedly mounted, so that connection steel wire pulls drive pulley by guiding fixed pulley
Rotation, so that protective cover is rotated around drive pulley stretches reset spring, so that parachute pack is contacted with air, in sky
Under the percussion of gas, parachute pack is opened, and increases air drag, reduces the speed of unmanned plane tenesmus, when unmanned plane slows down
Under fall to the ground after, since support rod is faced its upward thrust by ground, so that link block pushes mounting seat and flexible lamp
Pole is moved up along the lateral direction of guide sleeve, so that float electrode is in contact with stationary electrode, then makes Electromagnetic Control core
Another circuit of the heart is connected, by Electromagnetic Control core make compressed air bag discharge compressed air, by breather check valve into
Enter aerated rubber loop pad to inflate it, in this way can bumper and absorbing shock further protect unmanned machine part.
A kind of unmanned plane air crash protective device of the invention can promptly and accurately when unmanned plane failure is fallen
Parachute pack is popped up, air drag is increased, slows down the speed of unmanned plane tenesmus, the weight being subject to behind bottom surface so that unmanned plane falls
Power inertia force is substantially reduced with impact force, and then the floor stand of bottom can be played further after unmanned plane is contacted with bottom surface
Shock absorbing effect prevents unmanned plane components from loosening, to carry out unmanned plane protection.
Detailed description of the invention
By reading referring to attached drawing detailed description of non-limiting embodiments, other feature of the invention, purpose
It will be become more apparent upon with advantage.
In the accompanying drawings:
Fig. 1 is a kind of structural schematic diagram of unmanned plane air crash protective device of the present invention.
Fig. 2 is a kind of structural plan figure of reduction of speed buffer protection device of the present invention.
Fig. 3 is a kind of detailed construction schematic diagram of reduction of speed buffer protection device of the present invention.
Fig. 4 is the structure enlargement diagram of A in Fig. 3 of the present invention.
Fig. 5 is the structure enlargement diagram of B in Fig. 3 of the present invention.
Fig. 6 is a kind of working state figure of reduction of speed buffer protection device of the present invention.
In figure: mechanical arm -1, auxiliary rotatable paddle wheel -2, power paddle wheel -3, observation camera -4, support is fixedly mounted
Bar -5, reduction of speed buffer protection device -6, outside protective covers shell -61, Wind assistor mechanism -62, mechanical transition transmission mechanism -63, magnetic
Field action linkage mechanism -64, reduction gearing mechanism -65, overturning transition mechanism -66, compression pushing mechanism -67, damping gear
Structure -68, turned flabellum -621, connection shaft -622, linkage scroll bar -623, cooperation turbine -624, connection belt -625, connection
Turn column -626, repeatedly sliding block -631, connection push rod -633, linkage gear -634, movable rack -635, store sliding chute rod -632
Battery -641, electrode collar -643, dynamic cathode contact -644, resets disc spring -645, determines cathode contact-field coil -642
646, fixed electromagnet -651, moving armature -652, limit sliding rail -653, mandril -654, parachute pack -655, connection steel
Silk -661, guiding fixed pulley -662, drive pulley -663, protective cover -664, reset spring -665, link block -671, installation bottom
Seat -672, float electrode -673, guide sleeve -674, stationary electrode -675, Electromagnetic Control core -681, compressed air bag -682,
Breather check valve -683, aerated rubber loop pad -684.
Specific embodiment
To be easy to understand the technical means, the creative features, the aims and the efficiencies achieved by the present invention, below with reference to
Specific embodiment, the present invention is further explained.
As shown in Fig. 1-6 figure, the present invention provides a kind of technical solution of unmanned plane air crash protective device:
A kind of unmanned plane air crash protective device, structure include that mechanical arm 1, auxiliary rotatable paddle wheel 2, type drive paddle is fixedly mounted
Impeller 3, observation camera 4, support rod 5, reduction of speed buffer protection device 6, described one end that mechanical arm 1 is fixedly mounted are equipped with dynamic
Power paddle wheel 3 and it is connected by way of rotation, the other end that mechanical arm 1 is fixedly mounted and reduction of speed buffer protection fill
It sets 6 outer surface to be connected by way of bonding, the front of the auxiliary rotatable paddle wheel 2 is equipped with power paddle wheel 3, described
Observation camera 4 is installed on the bottom end that mechanical arm 1 is fixedly mounted and is connected by welding, and the support rod 5 is set
In reduction of speed buffer protection device 6 bottom end and be connected by way of bonding, it is described observation camera 4 surface be equipped with
Power paddle wheel 3, the reduction of speed buffer protection device 6 include outside protective covers shell 61, Wind assistor mechanism 62, mechanical transition transmission
Mechanism 63, magnetic fields linkage mechanism 64, reduction gearing mechanism 65, overturning transition mechanism 66, compression pushing mechanism 67, damping connection
The inside of motivation structure 68, the outside protective covers shell 61 is connected embedded with Wind assistor mechanism 62 and by way of rotation, institute
The right side for stating Wind assistor mechanism 62 is equipped with mechanical transition transmission mechanism 63 and is connected by way of sliding, the machine
The top of tool transition transmission mechanism 63 is equipped with magnetic fields linkage mechanism 64 and by mechanical connection, the reduction gearing mechanism
65 are installed on the surface of magnetic fields linkage mechanism 64 and are connected by electric signal, and the magnetic fields linkage mechanism 64 is pacified
It is connected loaded on the lower section for overturning transition mechanism 66 and by way of rotation, the two sides installation of the reduction gearing mechanism 65
There is overturning transition mechanism 66 and be connected by way of bonding, the compression pushing mechanism 67 and damping linkage mechanism 68 are logical
It crosses electric signal to be connected, the right side of the damping linkage mechanism 68 is equipped with mechanical transition transmission mechanism 63 and by mechanical mistake
Connection is crossed, the Wind assistor mechanism 62 is equipped with turned flabellum 621, connection shaft 622, linkage scroll bar 623, cooperation turbine
624, belt 625, linkage rotary column 626 are connected, the top of the turned flabellum 621 is embedded with one end of connection shaft 622 simultaneously
And be connected by way of rotation, the other end of the connection shaft 622 is connected by welding with linkage scroll bar 623
It connects, the back side of the linkage scroll bar 623 is equipped with cooperation turbine 624 and is rotatablely connected by way of engagement, the cooperation whirlpool
Wheel 624 is rotatablely connected by connection belt 625 and linkage rotary column 626, the linkage rotary column 626 and mechanical transition transmission mechanism 63
It is connected by way of sliding, the machinery transition transmission mechanism 63 is equipped with repeatedly sliding block 631, sliding chute rod 632, connection push rod
633, linkage gear 634, movable rack 635, the sliding block repeatedly 631 are installed on the outer surface of linkage rotary column 626 and pass through
The mode of sliding is connected, and the outside of the sliding chute rod 632 is nested and is connected by way of sliding with sliding block 631 repeatedly
It connects, one end of the connection push rod 633 is fixedly installed in repeatedly the front surface of sliding block 631 and is connected by way of rotation
Connect, the other end of the connection push rod 633, which is set to, linkage gear 634 and to be rotatablely connected, the outside of the linkage gear 634 with
Movable rack 635 is meshed, and the movable rack 635 is connect with magnetic fields linkage mechanism 64 by mechanical transition, the work
Carry-over bar 635 and damping linkage mechanism 68 are mechanically connected, and the magnetic fields linkage mechanism 64 is equipped with battery 641, magnetic field line
Circle 642, dynamic cathode contact 644, resets disc spring 645, determines cathode contact 646 electrode collar 643, the battery 641 it is upper
Side is equipped with field coil 642 and is connected by electric signal, and the inside of the field coil 642 is embedded with electrode collar 643, institute
The back side for stating electrode collar 643, which is equipped with, to be resetted disc spring 645 and is connected by way of bonding, the electrode collar 643
Outer surface is connected by welding with dynamic cathode contact 644, and the top of the dynamic cathode contact 644, which is equipped with, determines cathode touching
Point 646, it is described to determine cathode contact 646 and be connected with reduction gearing mechanism 65 by electric signal, the electrode collar 643 be turned over
It crosses mechanism 66 and passes through mechanical transition connection, the reduction gearing mechanism 65 is equipped with fixed electromagnet 651, moving armature 652, limit
Sliding rail 653, mandril 654, parachute pack 655, the fixed electromagnet 651 are connected with cathode contact 646 is determined, the fixation
The top of electromagnet 651 is equipped with moving armature 652 and is connected by magnetic force, the top of the moving armature 652 and mandril
654 are connected by welding, and the moving armature 652 is connected by way of sliding with limit sliding rail 653, described
The outer surface for limiting sliding rail 653 is connected by way of bonding with overturning transition mechanism 66, the top installation of the mandril 654
There is parachute pack 655 and be connected by way of fitting, the overturning transition mechanism 66 is equipped with connection steel wire 661, leads
To fixed pulley 662, drive pulley 663, protective cover 664, reset spring 665, the connection steel wire 661 and guiding fixed pulley 662
Outside be connected by way of rolling, the other end of the connection steel wire 661, which is set to, drive pulley 663 and passes through rotation
Mode be connected, the drive pulley 663 and the bottom end of protective cover 664 are rotatablely connected, one end of the reset spring 665 with
The inside of protective cover 664 is connected by way of bonding, and the other end and sliding rail 653 of the reset spring 665 pass through welding
Mode be connected, it is described connection steel wire 661 head end be connected with electrode collar 643, the compression pushing mechanism 67 equipped with company
Block 671, mounting seat 672, float electrode 673, guide sleeve 674, stationary electrode 675 are connect, the top of the link block 671 is equipped with
Mounting seat 672 and it is connected by way of bonding, the inside of the mounting seat 672 is equipped with float electrode 673, institute
The inside for stating guide sleeve 674 is connected by way of nested with stationary electrode 675, the mounting seat 672 and guide sleeve 674
It is connected by way of sliding, the stationary electrode 675 is connected with damping linkage mechanism 68 by electric signal, the damping
Linkage mechanism 68 is equipped with Electromagnetic Control core 681, compressed air bag 682, breather check valve 683, aerated rubber loop pad 684, institute
It states Electromagnetic Control core 681 to be connected with stationary electrode 675 by electric signal, the right side installation of the Electromagnetic Control core 681
There is movable rack 635 and connected by mechanical transition, the bottom end of the Electromagnetic Control core 681 is equipped with compressed air bag 682
And it is connected by welding, the compressed air bag 682 is connected with breather check valve 683, and the air inlet is unidirectional
Valve 683 is embedded in the inside for being installed on aerated rubber loop pad 684.
A kind of unmanned plane air crash protective device of the invention, its working principle is that: when unmanned plane failure air crash, due to by
To the influence of gravity, so that unmanned plane accelerates tenesmus, so that stronger wind-force can be generated around unmanned plane, and wind-force overcomes connection
Biggish stiction drives turned flabellum 621 to rotate between shaft 622 and outside protective covers shell 61, so that co-axial
Connection shaft 622, which follows, to be rotated together, and is driven and is rotated with the linkage scroll bar 623 for connecting the welding of 622 phase of shaft, so that with linkage whirlpool
The cooperation turbine 624 that bar 623 is meshed rotates, then by connection 625 transmitting rotary power of belt, so that with belt is connect
The 625 linkage rotary columns 626 being connected follow rotation, so that linkage rotary column 626 drives repeatedly sliding block 631 along sliding chute rod
632 outer surface slides up and down, so that pushing linkage tooth with the movement of connection push rod 633 that 631 front surface of sliding block is connected repeatedly
634 rotation of wheel, drives the movable rack 635 being meshed with linkage gear 634 to move up, makes battery 641 and Electromagnetic Control
Core 681 is connected, and Electromagnetic Control core 681 controls field coil 642 and obtains electric generation field of magnetic forece, and electrode collar 643 is pushed to drive
Dynamic cathode contact 644 rotates, and compression resets disc spring 645, while making dynamic cathode contact 644 and determining 646 phase of cathode contact
Contact, fixed electromagnet 651 is conductive to generate repulsion, the side for pushing moving armature 652 to drive mandril 654 along limit sliding rail 653
To upward sliding, parachute pack 655 is ejected, while electrode collar 643 drives one end rotation for the connection steel wire 661 being fixedly mounted
Take-up, so that connection steel wire 661 pulls drive pulley 663 to rotate by guiding fixed pulley 662, so that protective cover 664 is around biography
The rotation of movable belt pulley 663 stretches reset spring 665, so that parachute pack 655 is contacted with air, in the percussion of air
Under, parachute pack 655 is opened, and air drag is increased, and reduces the speed of unmanned plane tenesmus, is fallen to the ground when under unmanned plane deceleration
Afterwards, its upward thrust is faced by ground due to support rod 5, so that link block 671 pushes mounting seat 672 and float electrode
673 move up along the lateral direction of guide sleeve 674, so that float electrode 673 is in contact with stationary electrode 675, then make
Another circuit of Electromagnetic Control core 681 is connected, and makes the release compression of compressed air bag 682 empty by Electromagnetic Control core 681
Gas is inflated it by breather check valve 683 into aerated rubber loop pad 684, in this way can bumper and absorbing shock further protect nothing
Man-machine part.
Problems solved by the invention is the prior art when unmanned plane failure air crash, for the guarantor of UAV Components
Shield measure is not perfect, can not unload shield of trying hard to keep in time, cause unmanned plane when falling, since suffered inertia force is big, directly with ground
Face collision causes unmanned plane to damage, and unmanned plane is landing when ground, generates biggish impact force, easily leads to inside unmanned plane
Components occur to loosen and shift, and influence the function of unmanned plane, and the present invention is combined with each other by above-mentioned component, is gone out in unmanned plane
When existing failure is fallen, can pop-up parachute pack promptly and accurately, increase air drag, slow down the speed of unmanned plane tenesmus,
Gravity inertial power and the impact force being subject to behind bottom surface so that unmanned plane falls substantially reduce, then after unmanned plane and bottom surface contact
The floor stand of bottom can further play shock absorbing effect, prevent unmanned plane components from loosening, to carry out unmanned plane
Protection.
The above shows and describes the basic principles and main features of the present invention and the advantages of the present invention, for this field skill
For art personnel, it is clear that invention is not limited to the details of the above exemplary embodiments, and without departing substantially from spirit of the invention or
In the case where essential characteristic, the present invention can be realized in other specific forms.Therefore, in all respects, should all incite somebody to action
Embodiment regards exemplary as, and is non-limiting, the scope of the present invention by appended claims rather than on state
Bright restriction, it is intended that including all changes that fall within the meaning and scope of the equivalent elements of the claims in the present invention
It is interior.Any reference signs in the claims should not be construed as limiting the involved claims.
In addition, it should be understood that although this specification is described in terms of embodiments, but not each embodiment is only wrapped
Containing an independent technical solution, this description of the specification is merely for the sake of clarity, and those skilled in the art should
It considers the specification as a whole, the technical solutions in the various embodiments may also be suitably combined, forms those skilled in the art
The other embodiments being understood that.
Claims (8)
1. a kind of unmanned plane air crash protective device, structure includes that mechanical arm (1), auxiliary rotatable paddle wheel (2), power are fixedly mounted
Paddle wheel (3), observation camera (4), support rod (5), reduction of speed buffer protection device (6), it is characterised in that: the fixed installation
One end of mechanical arm (1) is equipped with power paddle wheel (3) and is connected by way of rotation, the fixed installation mechanical arm
(1) the other end is connected by way of bonding with the outer surface of reduction of speed buffer protection device (6), the auxiliary rotatable paddle wheel
(2) front is equipped with power paddle wheel (3), and observation camera (4) is installed on the bottom end of fixed installation mechanical arm (1) simultaneously
And be connected by welding, the support rod (5) is set to the bottom end of reduction of speed buffer protection device (6) and passes through bonding
Mode be connected, it is described observation camera (4) surface be equipped with power paddle wheel (3)；
The reduction of speed buffer protection device (6) includes outside protective covers shell (61), Wind assistor mechanism (62), mechanical transition driver
Structure (63), magnetic fields linkage mechanism (64), reduction gearing mechanism (65), overturning transition mechanism (66), compression pushing mechanism
(67), damping linkage mechanism (68), the inside of the outside protective covers shell (61) is embedded with Wind assistor mechanism (62) and by turning
Dynamic mode is connected, and mechanical transition transmission mechanism (63) is equipped on the right side of the Wind assistor mechanism (62) and passes through cunning
Dynamic mode is connected, and the top of the machinery transition transmission mechanism (63) is equipped with magnetic fields linkage mechanism (64) and passes through
Mechanical connection, the reduction gearing mechanism (65) are installed on the surface of magnetic fields linkage mechanism (64) and pass through electric signal
Connection, the magnetic fields linkage mechanism (64) are installed on the lower section of overturning transition mechanism (66) and the phase by way of rotation
Connection, the two sides of the reduction gearing mechanism (65) are equipped with overturning transition mechanism (66) and are connected by way of bonding
It connects, the compression pushing mechanism (67) is connected with damping linkage mechanism (68) by electric signal, the damping linkage mechanism
(68) mechanical transition transmission mechanism (63) is installed and by mechanical transition connection on the right side of.
2. a kind of unmanned plane air crash protective device according to claim 1, it is characterised in that: the Wind assistor mechanism
(62) turned flabellum (621), connection shaft (622), linkage scroll bar (623), cooperation turbine (624), connection belt are equipped with
(625), it links rotary column (626), the top of the turned flabellum (621) embedded with one end of connection shaft (622) and leads to
The mode for crossing rotation is connected, and the other end of connection shaft (622) is connected by welding with linkage scroll bar (623)
It connects, the back side of linkage scroll bar (623) is equipped with cooperation turbine (624) and is rotatablely connected by way of engagement, described to match
Turbine (624) are closed by connecting belt (625) and linkage rotary column (626) rotation connection, the linkage rotary column (626) and machinery mistake
Transmission mechanism (63) is crossed to be connected by way of sliding.
3. a kind of unmanned plane air crash protective device according to claim 1, it is characterised in that: the machinery transition driver
Structure (63) is equipped with repeatedly sliding block (631), sliding chute rod (632), connection push rod (633), linkage gear (634), movable rack
(635), the sliding block repeatedly (631) is installed on the outer surface of linkage rotary column (626) and is connected by way of sliding, institute
The outside for stating sliding chute rod (632) is nested with sliding block repeatedly (631) and is connected by way of sliding, the connection push rod
(633) one end is fixedly installed in repeatedly the front surface of sliding block (631) and is connected by way of rotation, and the connection pushes away
The other end of bar (633) is set to linkage gear (634) and is rotatablely connected, the outside of the linkage gear (634) and movable teeth
Item (635) is meshed, and the movable rack (635) is connect with magnetic fields linkage mechanism (64) by mechanical transition, the work
Carry-over bar (635) and damping linkage mechanism (68) are mechanically connected.
4. a kind of unmanned plane air crash protective device according to claim 1, it is characterised in that: the magnetic fields gear
Structure (64) is equipped with battery (641), field coil (642), electrode collar (643), dynamic cathode contact (644), resets disc spring
(645), determine cathode contact (646), field coil (642) is installed above the battery (641) and passes through electric signal
It is connected, the inside of the field coil (642) is embedded with electrode collar (643), and the back side of the electrode collar (643), which is equipped with, resets circle
Disk spring (645) and it is connected by way of bonding, the outer surface and dynamic cathode contact (644) of the electrode collar (643)
It is connected by welding, the top of the dynamic cathode contact (644), which is equipped with, determines cathode contact (646), described to determine cathode
Contact (646) is connected with reduction gearing mechanism (65) by electric signal, the electrode collar (643) and overturning transition mechanism (66)
It is connected by mechanical transition.
5. a kind of unmanned plane air crash protective device according to claim 1, it is characterised in that: the reduction gearing mechanism
(65) fixed electromagnet (651), moving armature (652), limit sliding rail (653), mandril (654), parachute pack are equipped with
(655), the fixed electromagnet (651) is connected with cathode contact (646) is determined, and sets above the fixed electromagnet (651)
There is moving armature (652) and be connected by magnetic force, the top and mandril (654) of the moving armature (652) pass through welding
Mode be connected, the moving armature (652) is connected by way of sliding with limit sliding rail (653), limit cunning
The outer surface of rail (653) is connected by way of bonding with overturning transition mechanism (66), the top installation of the mandril (654)
There is parachute pack (655) and is connected by way of fitting.
6. a kind of unmanned plane air crash protective device according to claim 1 or 4, it is characterised in that: the overturning transition machine
Structure (66) is equipped with connection steel wire (661), guiding fixed pulley (662), drive pulley (663), protective cover (664), reset spring
(665), connection steel wire (661) is connected by way of rolling with the outside for being oriented to fixed pulley (662), the connection steel
The other end of silk (661) is set to drive pulley (663) and to be connected by way of rotation, the drive pulley (663) with
The bottom end of protective cover (664) is rotatablely connected, and passes through bonding on the inside of one end and protective cover (664) of the reset spring (665)
Mode be connected, the other end of the reset spring (665) is connected by welding with sliding rail (653), the company
The head end for connecing steel wire (661) is connected with electrode collar (643).
7. a kind of unmanned plane air crash protective device according to claim 1, it is characterised in that: the compression pushing mechanism
(67) link block (671), mounting seat (672), float electrode (673), guide sleeve (674), stationary electrode (675), institute are equipped with
The top for stating link block (671) is equipped with mounting seat (672) and is connected by way of bonding, the mounting seat
(672) inside is equipped with float electrode (673), and the inside of the guide sleeve (674) passes through nested with stationary electrode (675)
Mode is connected, and the mounting seat (672) is connected by way of sliding with guide sleeve (674), the stationary electrode
(675) it is connected with damping linkage mechanism (68) by electric signal.
8. a kind of unmanned plane air crash protective device described according to claim 1 or 3 or 7, it is characterised in that: the damping linkage
Mechanism (68) is equipped with Electromagnetic Control core (681), compressed air bag (682), breather check valve (683), aerated rubber loop pad
(684), the Electromagnetic Control core (681) is connected with stationary electrode (675) by electric signal, the Electromagnetic Control core
(681) movable rack (635) is installed and by mechanical transition connection, the bottom of the Electromagnetic Control core (681) on the right side of
End is equipped with compressed air bag (682) and is connected by welding, the compressed air bag (682) and breather check valve
(683) it is connected, breather check valve (683) insertion is installed on the inside of aerated rubber loop pad (684).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810920264.7A CN109204836A (en) | 2018-08-14 | 2018-08-14 | A kind of unmanned plane air crash protective device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810920264.7A CN109204836A (en) | 2018-08-14 | 2018-08-14 | A kind of unmanned plane air crash protective device |
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| Publication Number | Publication Date |
|---|---|
| CN109204836A true CN109204836A (en) | 2019-01-15 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810920264.7A Withdrawn CN109204836A (en) | 2018-08-14 | 2018-08-14 | A kind of unmanned plane air crash protective device |
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| CN (1) | CN109204836A (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110702998A (en) * | 2019-11-09 | 2020-01-17 | 重庆市辐射技术服务中心有限公司 | Electromagnetic radiation monitoring system based on mobile terminal and monitoring method thereof |
| CN111086640A (en) * | 2020-03-06 | 2020-05-01 | 国网福建省电力有限公司三明供电公司 | Automatic inspection unmanned aerial vehicle based on visual identification |
| ES2779633A1 (en) * | 2019-02-18 | 2020-08-18 | Artifact Consulting Slu | Massive Battle Royale-style robotic combat system (Machine-translation by Google Translate, not legally binding) |
| CN112173111A (en) * | 2020-11-05 | 2021-01-05 | 娄底市速尔成科技有限公司 | Internet-based carrying unmanned aerial vehicle |
| CN112373699A (en) * | 2020-10-22 | 2021-02-19 | 刘占波 | Unmanned aerial vehicle anti-falling device |
| CN112455704A (en) * | 2020-12-07 | 2021-03-09 | 国网河北省电力有限公司雄安新区供电公司 | Single screw unmanned aerial vehicle prevent weighing down device |
| TWI759797B (en) * | 2020-07-06 | 2022-04-01 | 中光電智能機器人股份有限公司 | Drone with parachute and control method thereof |
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2018
- 2018-08-14 CN CN201810920264.7A patent/CN109204836A/en not_active Withdrawn
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| ES2779633A1 (en) * | 2019-02-18 | 2020-08-18 | Artifact Consulting Slu | Massive Battle Royale-style robotic combat system (Machine-translation by Google Translate, not legally binding) |
| CN110702998A (en) * | 2019-11-09 | 2020-01-17 | 重庆市辐射技术服务中心有限公司 | Electromagnetic radiation monitoring system based on mobile terminal and monitoring method thereof |
| CN111086640A (en) * | 2020-03-06 | 2020-05-01 | 国网福建省电力有限公司三明供电公司 | Automatic inspection unmanned aerial vehicle based on visual identification |
| TWI759797B (en) * | 2020-07-06 | 2022-04-01 | 中光電智能機器人股份有限公司 | Drone with parachute and control method thereof |
| CN112373699A (en) * | 2020-10-22 | 2021-02-19 | 刘占波 | Unmanned aerial vehicle anti-falling device |
| CN112373699B (en) * | 2020-10-22 | 2022-12-30 | 刘占波 | Unmanned aerial vehicle anti-falling device |
| CN112173111A (en) * | 2020-11-05 | 2021-01-05 | 娄底市速尔成科技有限公司 | Internet-based carrying unmanned aerial vehicle |
| CN112455704A (en) * | 2020-12-07 | 2021-03-09 | 国网河北省电力有限公司雄安新区供电公司 | Single screw unmanned aerial vehicle prevent weighing down device |
| CN112455704B (en) * | 2020-12-07 | 2022-10-04 | 国网河北省电力有限公司雄安新区供电公司 | Single screw unmanned aerial vehicle prevent weighing down device |
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Application publication date: 20190115 |
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